Rotating combustion products generator with turbulent fuel injection zone



July 11, 1950 P.'KOLLSMAN 2,514,874

ao'rmuc comsusnon PRODUCTS GENERATOR wrrn TURBULENT FUEL INJECTION ZONE Filed Aug. 24, 1945 2 Sheets-Shat 1 w i m INVENTOR. p401. Kazan/4A4 BY J;

J y 1950 P. KOLLSMAN 2,514,874

ROTATING comausnou PRODUCTS GENERATOR wrra TURBULENT FUEL INJECTION ZONE 2 Sheets-Sheet 2 Filed Au 24, 1945 INVENTOR. 241/4 KOLLSMAM Arroewzx Patented July 11, 1950 ROTATING COMBUSTION PRODUCTS GEN- ERATOR WITH TURBULENT FUEL INJEC- TION ZONE Paul Kollsman, New York, N. Y.

Application August 24, 1945, Serial No. 612,389

6 Claims. (CI. 60-41) This invention relates to a thermodynamic engine in which there is a continuous flow of the energy producing gas.

An object of the invention is the provision of a thermodynamic engine of high efllciency in which a gas is compressed, heated and expelled in a single rotating unit.

Another object of the invention is the provision of a thermodynamic engine in which compression and heating of a gas is effected in a rotating member without travel through stationary pas-.

sages.

Another object of the invention i provision of a thermodynamic engine having a self-rotating combined compressor and heating member.

Another object of the invention is a thermodynamic engine in which a gas enters a rotating member adjacent to the axis thereof, is compressed at the periphery by the action of centrifugal force upon the gas column and again expelled adjacent to the axis of the rotary member, with heat energy supplied to the gas in its compressed state adjacent to the periphery of the rotary member, with rotation of the rotary member secured by the reaction of the gas discharge, flow of gas from the member being maintained by the difference in density in the opposite radial paths.

Other objects and features of the invention will be readily apparent to those skilled in the art from the specification and appended drawings illustrating certain preferred embodiments in which: a

Figure 1 is a view partly in Vertical section or the engine according to the present invention with the rotor shown in elevation.

Figure 2 is an enlarged vertical sectional view of the engine with the collector- ,and nozzle broken away. the view being taken on line 11-11 of-Fig.1.

Figure 3 is a partial front elevational view,

partly in section and with the case broken away to show the internal rotor.

Figure 4 is a vertical sectional view similar to Figure 2 but showing a modified form of the invention.

Figure 5 is a partial detail form of intake'for the engine.

In the form of the invention shown in Figures 1, 2, vand 3,- there are shown a pair of casing sections I and '2'which combine to form an enlarged cylindrical chamber 3. Casing section I has an axial extension I forming an. intake duct, while casing section 2 has an axial extension 5 forming a collecting chamber 8 and a nomle portion 1.

view of a modified Within the duct 4 upon spider legs 8 is mounted a support 9 for a stationary shaft ll. Upon the shaft II by bearings l2 and I3 is mounted a rotor l4 formed of two half sections l5 and I6, joined together in spaced relation by pins I! so as to form an insulating air space between the sections. Adjacent to the axis of the rotor M the space between the sections is filled by an insulating ring I8.

Upon the rotor sections l5 and iii are mounted aligned fins I9 and 2|, serving to divide the space within chamber 3 into a plurality of individual chambers as shown more particularly in Figures 1 and 3. As shown in Figures 1 and 2, these chambers are of generally U shape with spaced radial legs and a connecting transverse bight. At the intake portion of the engine the fins 19 have portions 22 which extend generally axially of the engine and have their ends curved in the direction of rotation of the rotor to form scoops to pick up and direct the incoming gas into the chambers between the rotor fins. The fins 2| on the exit side of the engine are provided with portions 23 which extend generally axially of the rotor and have their ends curved away from the direction of rotation to serve as discharg nozzles.

Spaced about the periphery of the casing section I are a plurality of fuel injection nozzles 24 and ignitor plugs 25. Upon the stationary shaft II is mounted a stator 26 of an electric motor, the rotor 21 of which is mounted upon section l5 of rotor H. The wiring for the motor indicated at 28 leads through one of the spider legs 8 through support 9 and shaft II to the motor stator 26.

In the operation of the engine according to this invention the rotor I4 is initially rotated by the electric motor formed by the stator 26 and rotor 21 until it has been brought up to considerable speed. Thereafter fuel is injected into chamber 2 from the nozzles 24 and is ignited by the plugs 25. Thereafter the electric motor and the ignitor plugs may be de-energized, as combustion will thereafter be continuous and the rotor it selfd'riving.

The rotor It will operate at relatively high speeds at which the gas adjacent the periphery of the chamber 3 will be in a compressed state due to the action of centrifugal force upon the gas columns in the chamber legs between fins l9 and 2|. Due to the heating of the gas effected in the combustion chambers within chamber 3, the gas in the leg between fins 2| will be at a much higher temperature than the gas in the leg between fins l9 and thus at a much lower density.

the rotor l4 the major portion of their rotational energy, since they are moving in a direction of decreasing radius of rotation. Accordingly rotational energy which was transmitted to the incoming gas passing between fins l9 in adirection of increasing radius is substantially returned to the machine.

The portions 2: of fins 2| form discharge mtzles in a direction having a substantial tangential component and the reaction to the discharge serves to drive the rotor I 4. The scoop portions 22 of fins 19 assist the normal axial fiow in picking up and directing the incoming air or gas into the chambers between the fins l9.. The gases discharging from the nozzles formed between the portions 23 or the fins 2| are collected within chamber 6 and are discharged through the nozzle I in a continuous jet to secure an axial thrust, serving as a working force for the engine.

Of course it will be understood that, as in any rotating machinery, the working energy of the engine may be taken direct from the rotor 14 in conventional manner, in combination with or without utilizing the reactive jet force.

While direct fuel injection and ignition has been specifically illustrated in the drawing, it will be understood that the engine according to the invention will function with any means for introducing heat energy into the gas adjacent to the bight of the U-shaped gas path. When direct fuel injection is used, it is preferable to introduce the fuel immediately in advance of the end of the entrance leg of the U-shaped path, so as to insure more complete combustion of the fuel within the chamber 3.

In the modification of the invention shown in Figure 4, provision is made for the internal injection and ignition of the fuel and there is provided a floating casing about the rotor M to reduce the frictional loss occurring at the contact Iof the rotating air columns with the stationary casing. Like parts in Figure 4 have been given the same reference numerals as Figure 2. The fuel injection nozzle 24 and ignitor plugs 25 are now omitted and fuel injection is secured through the tube 3! extending through the spider leg 8, stationary support 9 and stationary shaft II to a discharge passage 32 leading from the shaft ll. Fuel sprayed through the passage 92 is collected within a circumferential groove 33 and a plurality of radial passage ways 36 extend toward the periphery of the rotor section and terminate in discharge nozzles 31 from which the fuel is sprayed into the chambers between fins IS.

The winding of the rotor 21 of the electric starting motor is connected to a sparkcoil 38 from which ignition wires 39 lead radially to ignitor plugs 4| adjacent the fuel discharge 'nozzles 31.

The casing sections l and 2, Figure 4, are made larger than those of Figure 2 to accommodate between the fins l9 and 2| and the interior walls in of the casing sections an intermediate floating 75 rotor casing 42 having only mechanical clearance with respect to the fins and the interior surfaces of the exterior casing. The casing 42 is free to rotate on bearings 43, of any desired type, as a follower to the rotation of the rotor I4. The casing 42 has been shown as a continuous piece of metal with the understanding that it can be soldered or welded in place about the rotor or may be joined in any desired manner. With the introduction of the casing 42' the frictional re- Sistance of the rotating gases with respect to the outer casing is greatly reduced so that the efilciency of the engine is increased. The operation of the engine of Figure 4 is identical with that described for the engines I, 2, and 3, the fuel now being supplied internally and the casing 42 following the rotation of the rotor l4 at fractional speed by frictional engagement with the rotary gases to reduce the frictional loss at the casing wall.

In the modification of the invention of Figure 5, for the spider legs 8 there have been substi tuted a plurality of directional vanes 45 which not only maintain the support 9 mechanically but serve to direct the incoming gas into a rotary path. In this modification the scoop portions 22 are omitted and therotor fins on the incoming side, indicated at 46, have straight ends since the incoming air or gas will be moving at substantially the same tangential yelocity as the entrance ends of the fins 'due to the directional vanes 45 through which the air is drawn by the axial flow.

While the drawings illustrate the bights of the U-shaped chambers as being relatively short, it will be understood that they may have a considerable axial extension to secure more complete combustion of the fuel while the air is at maximum compression. Also while the legs of the 49 chambers extending from the axis toward the periphery have been illustrated and referred to as radial, it will be understood that any directional path having a radial component may be used for these legs.

While certain preferred embodiments of the invention have been specifically disclosed, it is understood that the invention is not limited thereto, as many variations will be readily apparent to those skilled in the art and the invention is to be given its broadest possible interpretation within the terms of the following claims.

What is claimed is:

1. A combustion products generator comprising a stationary casing having an interior wall delining a rotor chamber, a rotor mounted for rotation within said chamber, said rotor including a body and a plurality of circumferentially spaced substantially radially extending blades on said body, said blades together with said body forming a plurality of substantially U-shaped rotor channels which together with the unbroken interior wall of the casing constitute individual and separate U-shaped passages, the legs of the U extending substantially radially, the bight of the U lying remote from the rotor axis, one leg constituting a compression passage and its end constituting an intake adjacent the rotor axis, theother leg constituting an expansion passage, and its end constituting an outlet adjacent the rotor axis, the outlet being directed at an angle to impart a tangential component to the direction of discharge of the combustion products tending to spin the rotor by reaction force, means the casing wall for injecting fuel into the channels adjacent the bight, whereby the fuel is intimately mixed with the compressed gas.

gas flowing through the channels by reason of the turbulence of the gase due tothe relative movement of the channels with respect to the casing, and means for igniting the resulting combustible mixture.

2. A combustion products generator comprising a stationary casing, a rotor mounted for rotation within said casing, said rotor including a body and a. plurality of circumferentially spaced substantially radially extending blades on said body, said blades together with said body forming a plurality of substantially U-shaped rotor channels which together with the unbroken interior wall of the casing constitute individual U-shaped passages, the legs of the U extendin substantially radially and the bight of the U lying remote from the rotor axis one leg constituting a compression passage and its end constituting an intake, the other legconstituting an expansion passage, andits end constituting an outlet, said body comprising two body portions, one body portion including said first leg and the other body portion including the second leg of the U-channel, the first body portion being separated from the second body portion by a -zone of reduced heat conductivity to retard the transfer of heat from one body portion to the other, means for injecting fuel into the rotor channels adjacent the bight, whereby the fuel is evenly distributed over the several channels and intimately mixed with the compressed gas flowing through the channels by reason of turbulence of the gas due to the relative movement of the channels with respect to the casing and the fuel injecting means, and means for igniting the resulting combustible fuel mixture.

3. "A combustion products generator comprising a casing having an interior .wall defining a rotor chamber, a rotor mounted for rotation within said chamber, said rotor including a body and a plurality of circumferentially spaced substantially radially extending blades on said body, said blades together with said body forming a plurality of substantially U-shaped rotor channels which together with the unbroken interior wall of the casing constitute individual and separate U-shaped passages, the legs of the u extending substantially radially andthe bight of the U lying remote from the rotor axis, one

leg constituting a compression passage and itswall of said shell constitute individual and separate U-shaped passages, the bight of the U lying remote from the rotor axis, one leg of the U constituting a compression passage and its end constitutingan intake adjacent the rotor axis, the other leg constituting an expansion passage, and its end constituting an outlet adjacent the rotor axis, said blades constituting continuous channel walls within the leg portion and the bight portion of said passages, means on said rotor for injecting fuel into the individual rotor -channels adjacent the bight, whereby the fuel is intimately mixed with the compressed gas flowing through the channels by reason of turbulence of the gas due to the relative movement of the channels with respect to the shell, the shell spinning at a lower rate than the rotor, and means on said rotor for igniting the combustible fuel mixture.

5. A combustion products generator comprising a casing having an interior wall defining a rotor chamber, a rotor within said chamber, said rotor including a body and a plurality of circumferentially spaced substantially radially extending blades on said body, said blades together with said body forming a plurality of substantially U-shaped rotor channels which together with the unbroken interior wall of the casing constituteindividual and separate U-shaped passages, the legs of the U extending substantially radially and the bight of the U lying remote from the rotor axis, one leg constituting a, compression passage and its end constituting an intake, the other leg constituting an expansion passage, and its end constituting an outlet, said blades constituting continuous channel walls within the leg portion and the bight portion of said passages, means for providing internal combustion within the rotor channels including means for injecting fuel into the individual rotor channels adjacent the bight, the injected fuel being intimately mixed with the compressed gas flowing through the channels by reason of the turbulence of the gas set up bythe relative movement of the channels with respect to the interior wall of the casing.

6. A combustion products generator comprising a casing having an interior wall defining a end constituting an intake adjacent the rotor axis, the other leg constituting an expansion passage, and its end constituting an outlet adjacent the rotor axis, said blades constituting continuous channel walls within the leg portion and the bight ortion of said passages, means on said rotor for injecting fuel into the individual rotor channels adjacent the bight, whereby the fuel is intimately mixed with the compressed gas flowing through the channels by reason of turbulence of the gas due to relative movement of the channels, with respect to the casing, and means on said rotor for igniting the combustible fuel mixture.

'4. A combustion Products generator comprising a casing, a, rotor within said casing, a freely rotatable shell between the rotor and the interior surface of the casing, said shell having an unbroken peripheral wall, said rotor including a body and a plurality of circumferentially spaced substantially radially extending blades on said body, said blades together with said body forming a plurality of substantially U-shaped rotor channels which together with the interior rotor chamber, arotor within said chamber, said rotor including a body and a plurality of circumferentially spaced substantially radially extending blades on said body, said blades together with said body forming a plurality of substantially U-shaped rotor channels which together the U-channel, the first body portion being separated from the second body portion by a, zone of reduced heat conductivity to retard the transfer of heat from one body portion to the other, means for providing internal combustion within the rotor channels includlngmeans for inject- .ing fuel into the individual rotor channels adjacent the bight, the injected fuel being intimately mixed with the compressed gas flowing through the channels by reason of the turbulence REFERENCES CITED The following references are of record in'the file of this patent:

UNITED STATES PATENTS Number Name Date 1,256,674 Fiittinger Feb. 19, 1918 2,256,198 Hahn Sept. 16, 1941 2,272,676 L'educ Feb. 10, 1942 8 Number Name Date 2,283,176 Birmann May 19, 1942 2,334,625 Heppner Nov. 16, 1943 5 FOREIGN m'mn'rs Number Country Date 5317,4113 Great Britain June 24, 1941 OTHER REFERENCES "Steam and Gas Turbines," by A. Stodola, translated by L. C. Lowenstein, published 1927 by McGraw-Hill Book 00., New York, New York, volume 11, p ges 1220-1221. S 

